Method of repairing composite edge structures

Abstract

The application discloses a composite material edge structure repairing method, which comprises the following steps: manufacturing a support back plate with the same shape as the edge structure of the composite material to be repaired; fixing an expansion material with the same material as the edge structure of the composite material to be repaired on the back of the support back plate to manufacture an expansion structure; fixing the expansion structure at the edge of the edge structure of the composite material and symmetrically arranging the expansion structure with the edge structure of the composite material; and heating and curing the edge structure of the composite material by using a heating and curing system to repair the edge structure of the composite material. In the application, the resin glue or glue film can be accurately controlled according to the required curing temperature, so that the resin glue or glue film is fully cured and reaches the best performance, and the structural strength of the repairing area is ensured.

Description

Technical Field

[0001] This invention relates to the field of repair technology, and in particular to a method for repairing the edge structure of composite materials. Background Technology

[0002] Composite material structures are widely used in the aerospace industry due to their superior high stiffness, high strength, lightweight, and excellent design performance, especially in civil aircraft, where the proportion of composite structural components is continuously increasing. However, in actual maintenance work, it is often necessary to perform heat curing repairs on damaged areas. When the damaged area involves edge structures, the temperature within the heated area is difficult to maintain consistently due to the thermal conductivity of the edge structures.

[0003] Existing manufacturer solutions typically only use vacuum negative pressure devices and heating curing systems to heat and cure composite materials for repair.

[0004] However, existing technologies for heat curing composite material structures do not adequately consider heat loss and structural differences in edge areas. Due to structural differences, their thermal insulation and conductivity naturally vary, making it difficult to achieve temperature uniformity across the entire temperature control zone. This can lead to localized overheating, damaging the repaired parts, or insufficient localized temperatures, preventing the adhesive or film from fully curing, thus affecting its performance and structural strength, ultimately resulting in repair failure. Summary of the Invention

[0005] The purpose of this invention is to provide a method for repairing the edge structure of composite materials, so as to successfully repair the edge area of ​​the composite material structure.

[0006] To address the aforementioned technical problems, the present invention provides the following technical solution:

[0007] A method for repairing the edge structure of a composite material includes the following steps:

[0008] Fabricate a support backplate with the same shape as the edge structure of the composite material to be repaired;

[0009] An extension material of the same material as the edge structure of the composite material to be repaired is laid and fixed to the back of the support back plate to create an extension structure.

[0010] The extended structure is fixed to the edge of the edge structure of the composite material, and the extended structure is arranged symmetrically with the edge structure of the composite material.

[0011] A heating and curing system is used to heat and cure the edge structure of the composite material in order to repair the edge structure of the composite material.

[0012] Preferably, when fabricating a support backplate with the same shape as the edge structure of the composite material to be repaired, the following steps are included:

[0013] By selecting an area with the same shape as the edge structure of the composite material in an undamaged region of the composite material's edge structure and laying glass fiber impregnated with resin;

[0014] Vacuum bags are placed over the areas of the composite material edge structure where glass fiber is laid, and vacuum curing is performed to complete the fabrication of the support backplate.

[0015] Preferably, when fabricating a support backplate with the same shape as the edge structure of the composite material to be repaired, a sheet metal forming process is used to make the metal sheet into the support backplate.

[0016] Preferably, when fabricating the extended structure by attaching and fixing an extension material of the same material as the edge structure of the composite material to be repaired to the back of the support backplate, the following steps are included:

[0017] Using a curing adhesive, an extension material of the same material as the edge structure of the composite material to be repaired is applied to the back of the support backplate.

[0018] The extension material and the support backplate are fitted together using a vacuum bag and then vacuumed to shape the extension material.

[0019] A heat curing system is used to heat and cure the extended material to create an extended structure.

[0020] Preferably, a heating and curing system is used to heat and cure the extended material to form an extended structure. Then, a cutting tool is used to cut the corners of the extended structure so that the extended structure can fit tightly with the edge structure of the composite material.

[0021] Preferably, a heating and curing system is used to heat and cure the extended material to form an extended structure, and then a grinder is used to grind the surface of the extended structure.

[0022] Preferably, when the extended structure is fixed to the edge of the edge structure of the composite material and the extended structure is symmetrically arranged with respect to the edge structure of the composite material, the following steps are included:

[0023] The extended structure is spliced ​​onto the edge of the edge structure of the composite material to make the extended structure and the edge structure of the composite material symmetrical;

[0024] The extended structure and the edge structure of the composite material are initially bonded and fixed together using adhesive tape;

[0025] A vacuum bag is used to fit the extended structure and the edge structure of the composite material together, and a vacuum treatment is performed to fix the extended structure and the edge structure of the composite material together.

[0026] Compared with existing technologies, the advantages of the composite material edge structure repair method of this invention are as follows:

[0027] In this invention, a support backing plate is first fabricated using the edge structure of the composite material. Then, using the support backing plate as a mold, an extension material of the same material as the edge structure of the composite material to be repaired is laid on the support backing plate to create an extension structure. Next, the extension structure is spliced ​​onto the edge of the edge structure of the composite material to make the extension structure symmetrical with the edge structure of the composite material. Therefore, when the edge structure of the composite material is heated and cured using a heating and curing system for repair work, the original edge of the composite material is moved outward due to the setting of the extension structure, so that the original edge of the composite material is located in the middle area of ​​the heating, thereby controlling the thermal conductivity of the original edge area and making the temperature of the heating area uniform. Thus, the curing temperature of the repair is controlled, and the resin or adhesive film can be precisely controlled according to the required curing temperature to ensure that it is fully cured, achieves optimal performance, and guarantees the structural strength of the repaired area. Attached Figure Description

[0028] Figure 1 This is a flowchart of a composite material edge structure repair method according to an embodiment of the present invention;

[0029] Figure 2 This is a top view of the edge structure and extended structure according to an embodiment of the present invention;

[0030] Figure 3 This is a side view of the edge structure and extended structure according to an embodiment of the present invention.

[0031] In the diagram, 1 represents the edge structure; 2 represents the extended structure. Detailed Implementation

[0032] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0033] In the description of this invention, it should be understood that the term "comprising" as used in this specification means the presence of the stated features, integers, steps, operations, parts, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, parts, components, and / or groups thereof. It should be understood that when we say a part is "connected" to another part, it can be directly connected to the other part, or there may be intermediate parts. The term "and / or" as used herein includes all or any unit and all combinations of one or more associated listed items.

[0034] like Figure 1 and Figure 3 As shown, this invention relates to a method for repairing the edge structure of a composite material, comprising the following steps:

[0035] Fabricate a support backplate with the same shape as the edge structure 1 of the composite material to be repaired;

[0036] An extension material of the same material as the edge structure 1 of the composite material to be repaired is laid and fixed to the back of the support back plate to create an extension structure 2.

[0037] The extension structure 2 is fixed to the edge of the edge structure 1 of the composite material, and the extension structure 2 is arranged symmetrically with the edge structure 1 of the composite material.

[0038] A heating and curing system is used to heat and cure the edge structure 1 of the composite material in order to repair the edge structure 1 of the composite material.

[0039] In this invention, a support backing plate is first fabricated using the edge structure 1 of the composite material. Then, using the support backing plate as a mold, an extension material of the same material as the edge structure 1 of the composite material to be repaired is laid on the support backing plate to create an extension structure 2. Next, the extension structure 2 is spliced ​​onto the edge of the edge structure 1 of the composite material to make the extension structure 2 symmetrical with the edge structure 1 of the composite material. Therefore, when the edge structure 1 of the composite material is heated and cured using a heating and curing system for repair work, the setting of the extension structure 2 moves the original edge of the composite material outward, placing the original edge of the composite material in the middle area of ​​the heating zone. This controls the thermal conductivity of the original edge area, making the temperature of the heating zone uniform. Thus, the curing temperature of the repair is controlled, allowing the resin or adhesive film to be precisely controlled at the required curing temperature, ensuring it is fully cured, achieving optimal performance, and guaranteeing the structural strength of the repaired area.

[0040] It should be noted that before performing heat curing repair, a structural analysis should be conducted on the edge area of ​​the composite material to be repaired. This analysis will determine the structure of the edge area and the required materials. This work can be done by consulting the manufacturer's manual, dissecting the structure of scrap parts, and summarizing previous experience in repairing this area. This will clearly reveal key information such as whether the edge structure of the composite material is a laminate structure or a honeycomb sandwich structure, the type of fiber material used, and the thickness of the panel layup.

[0041] In this embodiment, the following steps are included when fabricating a support backplate with the same shape as the edge structure 1 of the composite material to be repaired:

[0042] By selecting an area with the same shape as the edge structure 1 of the composite material in the undamaged area of ​​the edge structure 1, glass fiber impregnated with resin is laid on it.

[0043] Vacuum bags are placed over the area where glass fiber is laid on the edge structure 1 of the composite material, and vacuum curing is performed to complete the fabrication of the support back plate.

[0044] That is, a region with the same shape as the edge structure 1 of the composite material is selected in the undamaged area and glass fiber impregnated with resin is laid on it. Then, a vacuum bag is placed in this area and vacuum curing is performed to obtain a support backing plate with the same shape as the edge structure 1 of the composite material. Thus, when the extension structure 2 is laid on the support backing plate to make it, it can be ensured that the extension structure 2 has the same shape as the edge structure 1 of the composite material.

[0045] In other embodiments, when fabricating a support backplate with the same shape as the edge structure 1 of the composite material to be repaired, a sheet metal forming process is used to make the metal sheet into the support backplate.

[0046] In other words, the metal sheet can also be made into a support back plate with the same shape as the edge structure 1 of the composite material through sheet metal forming process, so that the support back plate has a strong structural strength.

[0047] In this embodiment, when laying and fixing an extension material of the same material as the edge structure 1 of the composite material to be repaired onto the back of the support back plate to create the extension structure 2, the following steps are included:

[0048] Using a curing adhesive, an extension material of the same material as the edge structure 1 of the composite material to be repaired is applied to the back of the support backplate;

[0049] The extension material and the support backplate are fitted together using a vacuum bag and then vacuumed to shape the extension material.

[0050] The extended material is heated and cured using a heating and curing system to form the extended structure 2.

[0051] That is, firstly, the extended material is laid on the back of the support back plate along the shape of the support back plate so that the shape of the extended material is the same as that of the edge structure 1 of the composite material. Then, a vacuum bag is used to fit the extended material and the support back plate together and vacuum treatment is performed to shape the extended material. Finally, the heating and curing system heats and cures the extended material to make a stable extended structure 2.

[0052] Preferably, after the extended material is heated and cured using a heating and curing system to form the extended structure 2, the edges and corners of the extended structure 2 are cut using a cutting tool so that the extended structure 2 can fit tightly with the edge structure 1 of the composite material, thus ensuring the smooth progress of subsequent repair work.

[0053] Furthermore, the extended material is heated and cured using a heating and curing system to form the extended structure 2. Then, the surface of the extended structure 2 is polished using a grinder to remove defects and burrs, so as to prevent the vacuum bag from being punctured during the vacuuming process.

[0054] In this embodiment, fixing the extension structure 2 to the edge of the edge structure 1 of the composite material and symmetrically arranging the extension structure 2 with the edge structure 1 of the composite material includes the following steps:

[0055] The extended structure 2 is spliced ​​onto the edge of the edge structure 1 of the composite material, so that the extended structure 2 and the edge structure 1 of the composite material are symmetrical.

[0056] The extended structure 2 and the edge structure 1 of the composite material are initially glued and fixed together using adhesive tape;

[0057] The extended structure 2 and the edge structure 1 of the composite material are fitted together using a vacuum bag and then vacuumed to fix the extended structure 2 and the edge structure 1 of the composite material together.

[0058] In other words, when splicing the extension structure 2 and the edge structure 1 of the composite material together, the two are first glued together with tape to fix them in place. Then, a vacuum bag is used to put the extension structure 2 and the edge structure 1 of the composite material together and vacuum treatment is performed so that the extension structure 2 and the edge structure 1 of the composite material can be firmly attached together, thereby ensuring the smooth progress of subsequent repair work.

[0059] In summary, the embodiments of the present invention provide a method for repairing the edge structure of a composite material. Compared with the prior art, the present invention takes into account the characteristic of high thermal conductivity at the edge of the component structure. By creating an extended area, the edge of the edge structure 1 of the composite material is moved outward, so that the edge of the original edge structure 1 of the composite material is in the middle position of the heating. This controls the thermal conductivity of the original edge area, thereby allowing the resin or adhesive film to be precisely controlled at the required curing temperature, so that it can be fully cured to achieve optimal performance and ensure the structural strength of the repaired area of ​​the edge structure 1 of the composite material.

[0060] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A method for repairing the edge structure of a composite material, characterized in that, Includes the following steps: Fabricate a support backplate with the same shape as the edge structure of the composite material to be repaired; An extension material of the same material as the edge structure of the composite material to be repaired is laid and fixed to the back of the support back plate to create an extension structure. The extended structure is fixed to the edge of the edge structure of the composite material, and the extended structure is arranged symmetrically with the edge structure of the composite material. A heating and curing system is used to heat and cure the edge structure of the composite material in order to repair the edge structure of the composite material.

2. The method for repairing the edge structure of composite materials according to claim 1, characterized in that, When fabricating a support backplate with the same shape as the edge structure of the composite material to be repaired, the following steps are included: By selecting an area with the same shape as the edge structure of the composite material in an undamaged region of the composite material's edge structure and laying glass fiber impregnated with resin; Vacuum bags are placed over the areas of the composite material edge structure where glass fiber is laid, and vacuum curing is performed to complete the fabrication of the support backplate.

3. The method for repairing the edge structure of composite materials according to claim 1, characterized in that, When fabricating a support backplate with the same shape as the edge structure of the composite material to be repaired, a sheet metal forming process is used to make the support backplate from a metal sheet.

4. The method for repairing the edge structure of composite materials according to claim 1, characterized in that, When fabricating an extended structure by attaching and fixing an extension material of the same material as the edge structure of the composite material to be repaired to the back of the support backplate, the following steps are included: Using a curing adhesive, an extension material of the same material as the edge structure of the composite material to be repaired is applied to the back of the support backplate. The extension material and the support backplate are fitted together using a vacuum bag and then vacuumed to shape the extension material. A heat curing system is used to heat and cure the extended material to create an extended structure.

5. The method for repairing the edge structure of composite materials according to claim 4, characterized in that, The extended material is heated and cured using a heating and curing system to form an extended structure. Then, the edges and corners of the extended structure are cut using a cutting tool to ensure that the extended structure fits tightly with the edge structure of the composite material.

6. The method for repairing the edge structure of composite materials according to claim 4, characterized in that, The extended material is heated and cured using a heating and curing system to form an extended structure. Then, the surface of the extended structure is polished using a polisher.

7. The method for repairing the edge structure of composite materials according to claim 1, characterized in that, When fixing the extension structure to the edge of the edge structure of the composite material and symmetrically arranging the extension structure with the edge structure of the composite material, the following steps are included: The extended structure is spliced ​​onto the edge of the edge structure of the composite material to make the extended structure and the edge structure of the composite material symmetrical; The extended structure and the edge structure of the composite material are initially bonded and fixed together using adhesive tape; A vacuum bag is used to fit the extended structure and the edge structure of the composite material together, and a vacuum treatment is performed to fix the extended structure and the edge structure of the composite material together.

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